Self-propelled illuminating missile with device for releasing a parachute at a selected point of its trajectory



R. J. M. BARES SELFPROPELLED ILLUMINATING MISSILE WITH DEVICE FOR RELEASING A PARACHUTE AT A SELECTED POINT OF ITS TRAJECTORY Filed June 1, 1959 Oct. 2, 1962 Hg. 7a

i i Q The invention relates to a self-propelled illuminating parachuted missile, of the type in which the outer packing is used as a mortar tube for starting the illuminating missile on the course of its trajectory, while the ignition of the illuminating chamber and the ejection of the parachute take place at the end of a period of the trajectory, this period being adjusted at a single value.

In known types of missiles, if the trajectory is too high, the range is reduced; and as the parachute drop begins too high up and the illumination ceases to function too soon before reaching the ground, the effectiveness of the missile is impaired.

yIf the trajectory is such that the height at which the parachute is released is correct, the distance along a vertical axis from the illuminated point to the tiring point is subject to little variation, which is an important requirement.

The application is thus restricted to the use of a series of missiles having stepped ranges, each range corresponding to a different missile.

This solution is costly from the supply point of view and complicates the problem of maintaining supplies to the users and thus reduces or eliminates the possibility of firing at the desired distance.

The object of the invention is an illuminating hand missile, self-propelled, with mortar-packing, and which overcomes these disadvantages by permitting of adjustment of the parachute-releasing delays and which produces effective illumination at stepped distances along a trajectory determined by a tiring angle which is subject to little variation in practice, while employing moreover a single missile instead of, for example, three diiferent models,

The device of the invention consists in particular of an illuminating missile which is self-propelled by means of a rocket device driving an assembly consisting of an illuminating-composition chamber, attached to a packed parachute so as to regulate its descent; means for igniting the illuminating chamber, with a time-dela and an ejection charge which, on exploding, causes said parachute to be separated from said chamber, the whole assembly of said missile being packed in known manner in a mortartube with detachable cover from which it is tired by means of a small ejector charge which is ignited by a known device at the will of the tirer. After a certain delay, this ignition also causes the propeling rocket to ignite the illuminating charge and an ejection charge which expels the said parachute, which unfolds together with the ignited illuminating chamber attached to the parachute, thus separating both the parachute and the illuminating chamber from the propulsion rocket, characterized in that the ignition of the ejection charge and of the illumination chamber is produced, with a variable delay, by the ring of the propulsion rocket, the duration of said delay being adjustable by the tirer as soon as the removal of the closure cover of the motar tube makes it possible to grip the rocket-casing which protrudes from the mortar-tube when the cover is removed, thus enabling the tirer to rotate the rocket through pre-determined angles which may be indicated between reference marks and a pointer or index, these being respectively carried by the tube and by the rocket. This rotation takes place about the general rates Patent axis of the missile, while the remainder of the illuminating missile is xed for rotation in the mortar-tube; this rotation regulates, by means of a known device, the duration of the delay between the ignition of the propelling charge and the moment at which the illuminating chamber and its parachute are separated from the propelling rocket, leave the propulsion trajectory and begin their descent over the target area at a distance from the rer which effectively corresponds to the distance set by the tirer and selected at a point between the maximum range corresponding to the energy supplied by the propelling charge of the rocket and the range corresponding to the minimum delay in ignition transmission between the ignition of the propelling charge and the ignition of the ejection charge.

In order that the invention may be more clearly understood, a form of embodiment is shown below with reference to the accompanying drawings, the description which follows being given by way of example and not in any sense by way of limitation.

The accompanying FIGURES 1 and 2 are respectively a partial longitudinal cross-section of the assembly of the missile in its mortar packing and a partial View of the base of the rotating head rigidly iixed to the propelling rocket, taken along a transverse plane AA.

For the sake of clarity of the drawing, FIG. 1 has been split up into two sections which can be joined together: FIG. la and FIG. lb.

The mortar-tube 1 used as a packing is constituted for example by a tube of duralumin which is closed by a base Z of the same metal provided with a threaded axial orifice 3 Which receives any standard ignition device capable of being actuated by the tirer. This device is of known type and is not shown for this reason.

The mortar-tube 1 used as a packing-container up to the moment of firing, is closed by a stamped cover 4 provided, in that portion which ts on to the extremity of the tube 1, with a stamped groove 5 in which is housed a toric sealing joint 6 of synthetic rubber or the like. For storing and transport purposes, this cover is secured in place by an adhesive tape 7 with a tearing portion 8, stuck astride the cover and the tube 1, which further improves the air-tightness.

This cover 4 is provided, in front of the section of the tube 1, with a housing for the propulsion unit of the missile.

The assembly of the missile which is contained in the mortar-tube and in its cover 4, is constituted as follows:

A cylindrical body 9 of duralumin tube is closed at the rear by a base 11 of plastic material tted in this tube 11, resting on its rear section and secured by means of three shear lugs 12 which pass through this tube.

The base 11 is traversed by an axial tube 13 which opens into the rear in a concentric conical housing 14 in which is arranged a felt packing ring 15 so as to provide a gas-tight seal.

This base 11 rests on the base 2 and thus closes a c0- axial cavity 16 in which is arranged in a thin, air-tight casing 17. The chamber-release charge '18 which is ignited by the detonator screwed into the passage 3 as required by the tirer, so as to expel the internal assembly from the mortar-casing tube 1.

The axial tube passes through the sheath in which the parachute 20 is housed.

This sheath is constituted by two cylindrical half-shells 19, the lateral surfaces of which are applied against the interior of the cylindrical body 9 and the sections of which rest at the bottom on a cardboard washer 21 of the same internal diameter as the tube 9, through the centre of which passes the axial tube 13 and rests on the base 11 of plastic material.

At the front end, the half-shells form a flat base 22 pierced at its center, on which is supported a spacing-tube s os 3 7 23 of cardboard, the external diameter of which corresponds to the internal diameter of the shells i9 and which rests at the bottom on a washer 24 of cardboard which keeps the parachute packed in its sheath.

This washer 24 holds the tube 13 which passes through said washer in a co-axial position and is provided with a free passage for a coiled metallic cable 25 forming a spring around the tube t3 in the compartment arranged between the base 22 and the washer by the spacingtube 23.

The cable 25 is on the one hand attached by one of its extremities 26 to a ring 27 on which are xed the extremities of the suspension cords 28 of the parachute and on the other hand, its other extremity is attached to a metallic U-member 29 which is xed across a steel washer 31 closing the extremity of the metallic casing 32 or the illuminating charge 33.

This cylindrical casing 32 is closed by insetting on the Washer 31 at its lower extremity and at its upper extremity by insetting round the periphery of an annular washer 3 of cardboard.

This assembly which constitutes the illuminating charnber is held in the body 9 by two annular washers 35 and 36 of cardboard which are themselves held by a iixed metallic base 37 which passes into and is supported by a projection 38 on the front section or" the body 9 which is rrnly assembled with the fixed metallic base 37 by means of lugs 39.

The rear face of the metallic base 37 is hollowed out to form a coaxial cylindrical housing di extended by a second coaxial housing 42 of smaller diameter, which receives a chamber-releasing charge 43 mounted in the shape of a ring and held by a washer 44 glued on the projection between the two housings 41 and 42.

The illuminating mass 33 is compressed in its casing 32 round a central tube 45 which opens at the rear through the Washer 31 and opens at the front end into the central orifice 46 of the Washers 35 and 36, the diameter of which is greater than the external diameter of said tube 45 and smaller than that of the orifice 47 of the Washer 341 which holds the illuminating mass.

The ignition tube 13 passes coaxially through the central tube 45.

In order to insulate the illuminating charge from heat during the ignition process when the missile is tired, the diameters of the tubes 13 and 45 are so designed that an empty annular passage 48 is formed between them.

In the ignition tube 13 are arranged relays of compressed black gunpowder with a central passage, these relays being two in number, for example 49 and Sii arranged so that 49 is placed in the rear end of this tube and 51 is placed towards its upper end.

The upper end of the ignition tube 13 is secured by means of a ange 52 and a nut 53 on the threaded extremity 54 of a hollow shaft 55 which is screwed into the bottom 37 and provided with a lock-nut washer 56 which is externally cylindrical and which is located in the housing containing the chamber-release charge 43.

The shaft 55 which is xed in the base 37 comprises above this latter a cylindrical portion 57 and a reinforced portion 58 which retain a rotating head 57 capable of rotating about this shaft end resting at its base on the base 37 by means of flat portions in contact.

This rotating head 59 terminates in a threaded portion 61 into which opens the passage 62 of the reinforced portion 58 thus forming a housing for an igniting charge 63 of compressed black gunpowder. On `the threaded portion 61 is screwed the metal collar 60 of the base 64 of the body 65 which encloses the propulsive charge 66.

This base 64 is pierced towards the rear with openings forming discharge nozzles 67, for example three in number.

At least one passage 68 through the xed screwed portions 60, 61 puts the space 62 in communication with an excess pressure chamber 69 constituted between the conanni necting portion 71 of the rotating head and a tubular errule 72 fixed around the base 64tand leaving towards the rear an annular passage 73 which communicates with the exterior.

The propulsion charge 66 is introduced into the body of the propulsion unit 65 and rests on the cover 64 and preferably provided with a peripheral play 74.

Passages 75 are formed in the base 64 so as to permit the nozzles 67 to communicate with a pastille 76 for igniting the propellent composition.

hihis igniting pastille is introduced or compressed into an axial channel 77 formed in the mass of this propulsive composition.

The quantity of propulsive composition, the gases of which are discharged through the nozzles 67 and ensure the propulsion of the illuminating missile, is provided so as to impart an initial rate of speed to the unit which is suicient to permit the parachute of the illuminating chamber to be released at a point along the trajectory of maximum range at a suitable height for the optimum illumination and at such a distance that the furthest point of the target area is lit up.

ln order that the duration of ight, at the end of which the illuminating charge and its parachute are separated from its propulsive portion, may be varied as desired by the tirer between this maximum distance and the minimum distance from the corresponding target area, an adjustable time-delay ignition device is formed by means of a channel 78 which is arranged around the shaft 55 in the orientatable portion 59 and filled with an ordinary mixture of a slow combustion composition 79.

This channel 73 opens into the space 69 across the surface 71 through an orice Sti normally shut oif by a thin sheet of tin or fusible alloy.

The channel is additionally provided with outlets 82, S3, 84, for example three in number, spaced in a circle in the rear flat face of the orientable portion 59.

This face rests on a Washer of cardboard for example, Which is glued so as to be rigidly fixed to the fixed portion 37 and pierced with a single hole 86 extended by a passage 37 up to the charge 453.

In the extreme positions in which 82 or 84 is brought oppositely facing 56 for the minimum or maximum ranges, a lug 88 comes into a position of abutment with the ends of a circular groove 89 (FIGS. 1b and 2).

The mean position which brings 83 into position oppositely facing the hole 56 is indicated for example by an ordinary ball device thrust by a spring 1 housed in one of the portions and not shown on the drawings, and in the course of its travel, passes into a hollowed portion 90 of the other portion 59.

These orientations are facilitated as soon as the cover 4 is lifted; the tirer may then grip the body 65 of the propulsion unit which is rigidly xed to the rotating head 59 and can then cause it to rotate with respect to the assembly Which is held fixed, contained in the tube 9.

The rotation of this tube 9 is prevented from taking place in the tube l, when this latter is held with one hand, While with the other hand, the propulsion unit is made to rotate, by the presence in the mortar-tube 1, of portions 91 punched-out towards the interior, between which are housed, when at rest, corresponding projections 92 embossed on the tube 9.

The guiding of the projectile in the mortar-tube 1 and its locking in position during the storing and transport are on the `other hand ensured by means of a circular bead 93 embossed on the tube 9 and having an external diameter which corresponds to the internal diameter of 1.

The method of operation is self-evident. After removing the tape 7 by pulling on the extremity 8, the tirer removes the cover 4 and, while holding the mortar-tube with one hand he rotates the propulsion unit with the other hand so as to adjust the delay to the distance selected. l

The tirer then actuates the detonator which is xed at the base of the mortar-tube while maintaining this latter so as to `be pointed in a suitable direction and at a suitable angle of slope, thus effecting the ignition of the charge 18 which acts upon the base 1l so as to project the assembly of the projectile from its packing which has the function of a mortar-tube.

The detonation of the charge i7 ignites the relay charge 49 and the flame spreads in a very short time through the tube 13 and the relay charge Si, then through the tube 55 to the charge 63. Passing through 62 and 68, the tiame of this charge then passes into the excess pressure chamber 69 and then, through the nozzles 67 and the passages 75, ignites the primer charge 76 which ignites the propulsion charge 66.

The combustion gases of this charge are then discharged through the nozzles 67 and through the gap 73 into the atmosphere and ensure the propulsion of the illuminating projectile.

At the same time, the ame escaping from the nozzles causes the sheet 8l to melt and ignites the detonating powder '79 of the channel '73, through the hole S3 uncovered by the melting of the sheet.

At the end of the time set by the adjustment and when the hole 82., 83, or 84 corresponding to the hole d6 of the washer S5 has been brought by adjustment to a position oppositely facing this latter, the iiarne spreads through said hole 86, through the passage 37, and ignites the charge 43.

The deflagration of this charge 43 through the chamber 41 forces the illuminating chamber constituted by the charge 33 into its casing 32 through the washers 35, 36. The effort of thrust is then transmitted by the half-shells 19 and the base 2l to the plastic base li.

' Under the effect of this thrust, the lugs l2 are sheared and the base lil is forced -beyond the tube 19, followed by the ejection of the half-shells encasing the parachute and of the illuminating chamber. At the moment of liring of the chamber-release charge 43, the charge 33 of the illuminating chamber has been ignited by the ame passing through the hole 47 and the central portion 47 of the washer 34.

The elements thus ejected slide round the axial tube 13 and, when they have left the tube 9, the washer 21 is separated from the half-shells 19 which corne apart, thus freeing the parachute 20 which unfolds while remaining attached by its suspension cords 28 to the extremity of the cable 25.

The cable unfolds, the effort being absorbed by the elasticity of the spirals. When the spirals are extended to the maximum, this cable brakes the residual movement of translation of the illuminating charge, which is attached by the hook 29 of its casing, the charge being supported by the cable during the descent of the parachute.

In the device of the invention, it has thus been made possible to adapt the fire control to a number of distances of the target to be illuminated, by means of a single missile. This feature is accompanied by the advantages of storage and protection of the projectile and of the cornbination of its tiring means in a single missile, the latter such advantages being possessed by known missiles of this type, namely, of the self-propelled reaction rocket type.

A further advantage results from the fact that the front propulsion unit of the illuminating projectile is so fixed that the portions enclosing the illuminating chamber and its parachute, together with their connecting elements and other elements, are arranged in a general cylindrical assembly which feathers the projectile. This latter is thus driven along its trajectory by tractive force, thus providing stability on its course up to the point where the parachute drop commences.

A number of modifications can naturally be made with respect to the materials, in particular those constituting the different portions, also with respect to the various forms of construction of the portions constituting the f5 assembly, construction of-detonators and their fuses and the relations between the various elements which may all give rise to alternative forms with respect to the example which has been described and illustrated, and without thereby departing from the spirit or the scope of the invention.

Instead of a parachuted illuminating chamber, a missile could be employed to drop a smoke-laying chamber by parachute, or an explosive chamber or, more generally, a parachuted charge having a number of different destinations and combining a number of the above-mentioned functions.

What I claim is:

l. In a projectile assembly, in combination, an elongated tubular housing having an open end and an opposed closed end; a first propellent charge carried by said housing in the interior thereof adjacent said closed end thereof; an elongated projectile located in said housing and movable out of the latter through said open end thereof, said charge rupon ignition projecting said projectile out of said housing, Said projectile having a front end in the region of said open end of said housing and a rear end adjacent to said first propellent charge and said projectile inciuding at said front end thereof a second propellent charge for propelling said projectile, said projectile further including an elongated passage means communicating with the interior of said housing adjacent said first propellent charge, extending longitudinally through the projectile, and communicating also with said second propellent charge, and transfer means lo-cated in said passage means for transferring along said passage means a flame from said first propellent charge after the latter is ignited to said second propellent charge for igniting said second propellent charge.

2. In a projectile, in combination, an elongated tubular casing having front and rear ends; closure means closing said rear end of said casing and being displaceable from said rear end of said casing upon application to said closure means of a predetermined force; a first propellent charge yconnected to said front end of said casing; a unit located in said casing between said closure means and said first propellent charge spaced rearwardly of the latter, said unit including a parachute and a combustible illuminating mass connected thereto; a second propellent charge located forwardly of said unit between the latter and said first propellent charge for driving, upon ignition of said second propellent charge, said unit rearwardly in said casing to force said closure means therefrom and discharge said unit through said rear end of said casing, said illuminating mass of said unit being ignited from said second propellent charge; and means located between said first and second propellent charges for igniting said second propellent charge from the cornbustion of said first propellent charge, said unit including an exterior longitudinally split shell in which said parachute is located, said second propellent charge urging the split shell rearwardly to displace said closure means and to discharge the illuminating mass and parachute from said casing through the rear end thereof and said split shell falling away from said parachute after the unit is discharged from said casing.

3. ln a projectile, in combination, an elongated tubular casing having a discharge end and an opposed end distant from said -discharge end; a unit located in said casing and adapted to be discharged from the latter through said discharge end thereof; a first propellent charge connected to said casing at said opposed end thereof for propelling the casing when said first propellent charge is ignited; a second propellent charge located between said unit and said first propellent charge for discharging said unit when said second propellent charge is ignited; adjustable ignition means located between said first and second propellant charges of igniting said second propellent charge from a flame derived from said first propellent charge after ignition of the latter,

said adjustable ignition means being adjustable for igniting said second propellent charge after a selected period of time an elongated tubular housing having an open end and an opposed closed end, said tubular casing being located in said housing; and a third propellent charge in said housing adjacent said closed end thereof between said closed end and said casing for projecting said casing together with said unit, said first and second propellent charges, and said ignition means from said housing upon ignition of said third charge, whereby said housing acts also as a mortar.

4. In a projectile as recited in claim 3, said adjustable ignition means including a body movable With respect to said casing to a plurality of different positions and formed with an elongated passage different lengths of which respectively communicate with said second propellent charge in said different positions of said body, and a combustible composition located in said passage so that depending upon the position of said body different lengths of said composition will be burned before said second propellent charge is ignited so as to provide different time intervals before ignition of said second propellent charge.

5. In a projectile according to claim 4, said body being turnable about the axis of said casing and said passage having a plurality of free end portions distributed along its length and placed in communication with said exposive charge respectively in said positions of said body.

6. In a projectile, in combination, a support carrying a propellent charge and having an end face adjacent thereto, said support being formed with a bore extending from said end face thereof to said propellent charge; a body connected to said support for movement With respect to said end face thereof to a plurality of different positions with respect to said support, said body having an end face adjacent and directed toward said end face of said support and said body having an exterior surface opposed to said end face thereof, said body Vbeing formed with a passage extending rst from said exterior surface toward said end face thereof, then extending along a predetermined path in said body Without reaching said end face thereof, and said passage including a plurality of passage portions extending from said path to said end face so that said passage communicates at said portions thereof `distributed along said path with said end face of said body and said portions of said passage respectively communicating with said bore of said support in said ditferent positions of said body; and a combustible composition filling said passage so that depending upon the position of said body a different length of composition in said passage will be consumed before a flame will reach through said bore to said charge to ignite the latter.

7. In a projectile, in combination, a support carrying a propellent charge and having an end face adjacent thereto, said support being formed with a bore extending from said end face thereof to said propellent charge; a body `connected to said support for movement with respect to said end face thereof to a plurality of different positions with respect to said support, said body having an end face adjacent and directed toward said end face of said support and said body having an exterior surface opposed to said end face thereof, said body being formed with a passage extending first from said exterior surface toward said end face thereof, then extending along a predetermined path in said body Without reaching said end face thereof, and said passage including a plurality of passage portions extending from said path to said end face so that said passage communicates at said portions thereof distributed along said path with said end face of said body and said portions of said passage respectively communicating With said bore of said support in said different positions of said body; a combustible composition filling said passage so that depending upon the position of said body a different length of composition in said passage will be consumed before a flame will reach through said bore to said charge to ignite the latter, said body being turnable with respect to said support about a predetermined axis and one of said end faces being formed with an arcuate groove extending along a circle Whose center is in said axis and the other of said end faces carrying a pin which extends into said groove, two of said positions of said body being determined by engagement of said pin with the ends of said groove, respectively.

8. In a projectile assembly, in combination, an elongated casing; a propellent charge connected to said ciasing at a front end thereof; a unit located in said casing adjacent a rear end thereof and adapted to be discharged through said rear end of said casing; an ignition tube extending longitudinally through said unit along the interior of said casing and forming part of a passage through which said propellent charge is ignited; and an inner tube forming the interior limit of said unit, said inner tube coaxially surrounding and spaced from said ignition tube so as to insulate said unit from heat Within said ignition tube.

References Cited in the le of this patent UNITED STATES PATENTS 1,774,535 Wiley Sept. 2, 1930 2,442,528 Beattie June l, 1948 2,538,333 Schermuly et al Jan. 16, 1951 2,718,191 Garrahan Sept. 20, 1955 2,785,632 Clauser et al Mar. 19, 1957 

